38912 Federal Register / Vol. 86, No. 139 / Friday, July 23, 2021 / Rules and Regulations 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(i) European Aviation Safety Agency 

(EASA) AD 2016–0028, dated February 15, 

2016. 

(ii) Zodiac Aerospace Service Bulletin SB 

025–64–13, Revision 0, dated November 23, 

2015. 

(iii) Zodiac Aerospace Service Bulletin SB 

025–64–13, Revision 1, dated January 19, 

2016. 

(3) For EASA AD 2016–0028, contact the 

EASA, Konrad-Adenauer-Ufer 3, 50668 

Cologne, Germany; telephone +49 221 8999 

000; email ADs@easa.europa.eu; internet 

www.easa.europa.eu. You may find this 

EASA AD on the EASA website at https://

ad.easa.europa.eu. For Zodiac Aerospace 

service information, contact Safran 

Aerosystems—Plaisir, 61 rue Pierre Curie 

CS20001, 78373 Plaisir Cedex, France; 

telephone (33) 1 61 34 23 23; fax (33) 1 61 

34 24 41; or at https://www.safranaerosystems.com. 

(4) You may view this service information 

at the FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood Pkwy., 

Room 6N–321, Fort Worth, TX 76177. For 

information on the availability of this 

material at the FAA, call 817–222–5110. This 

material may be found in the AD docket on 

the internet at https://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2021–0188. 

(5) You may view this material that is 

incorporated by reference at the National 

Archives and Records Administration 

(NARA). For information on the availability 

of this material at NARA, email fedreg.legal@

nara.gov, or go to https://www.archives.gov/ 

federal-register/cfr/ibr-locations.html. 

Issued on June 10, 2021. 

Ross Landes, 

Deputy Director for Regulatory Operations, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2021–15480 Filed 7–22–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–1179; Project 

Identifier AD–2020–00818–E; Amendment 

39–21638; AD 2021–14–11] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

General Electric Company (GE) CF6– 

80A and CF6–80C2 model turbofan 

engines. This AD was prompted by an 

inspection by the manufacturer that 

revealed cracking of the high-pressure 

turbine (HPT) rotor stage 1 disk. This 

AD requires visual inspection and 

fluorescent penetrant inspection (FPI) of 

the HPT thermal shield and, if cracking 

is detected, removal from service of the 

HPT thermal shield, HPT rotor stage 1 

disk and HPT rotor stage 2 disk. The 

FAA is issuing this AD to address the 

unsafe condition on these products. 

DATES: This AD is effective August 27, 

2021. 

ADDRESSES: For service information 

identified in this final rule, contact 

General Electric Company, 1 Neumann 

Way, Cincinnati, OH 45215; phone: 

(513) 552–3272; email: 

aviation.fleetsupport@ae.ge.com; 

website: www.ge.com. You may view 

this service information at the FAA, 

Airworthiness Products Section, 

Operational Safety Branch, 1200 District 

Avenue, Burlington, MA 01803. For 

information on the availability of this 

material at the FAA, call (781) 238– 

7759. It is also available at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2020– 

1179. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2020–1179; or in person at Docket 

Operations between 9 a.m. and 5 p.m., 

Monday through Friday, except Federal 

holidays. The AD docket contains this 

final rule, any comments received, and 

other information. The address for 

Docket Operations is U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE, Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Kevin M. Clark, Aviation Safety 

Engineer, ECO Branch, FAA, 1200 

District Avenue, Burlington, MA 01803; 

phone: (781) 238–7088; fax: (781) 238– 

7199; email: Kevin.M.Clark@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to all General Electric Company 

(GE) CF6–80A, CF6–80A1, CF6–80A2, 

CF6–80A3, CF6–80C2A1, CF6–80C2A2, 

CF6–80C2A3, CF6–80C2A5, CF6– 

80C2A5F, CF6–80C2A8, CF6–80C2B1, 

CF6–80C2B1F, CF6–80C2B1F1, CF6– 

80C2B1F2, CF6–80C2B2, CF6–80C2B2F, 

CF6–80C2B3F, CF6–80C2B4, CF6– 

80C2B4F, CF6–80C2B5F, CF6–80C2B6, 

CF6–80C2B6F, CF6–80C2B6FA, CF6– 

80C2B7F, CF6–80C2B8F, CF6– 

80C2D1F, CF6–80C2K1F, and CF6– 

80C2L1F model turbofan engines. The 

NPRM published in the Federal 

Register on February 22, 2021 (86 FR 

10496). The NPRM was prompted by an 

inspection by the manufacturer that 

revealed cracking of the HPT rotor stage 

1 disk caused by increased stress on the 

HPT rotor stage 1 disk as a result of 

flange-to-flange cracking on the HPT 

thermal shield. In the NPRM, the FAA 

proposed to require visual inspection 

and FPI of the HPT thermal shield and, 

if cracking is detected, removal from 

service of the HPT thermal shield, HPT 

rotor stage 1 disk and HPT rotor stage 

2 disk. The FAA is issuing this AD to 

address the unsafe condition on these 

products. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received comments from 

five commenters. The commenters were 

Atlas Air, Boeing Commercial Airplanes 

(Boeing), Delta Air Lines (Delta), United 

Airlines (United) and the Air Line Pilots 

Association, International (ALPA). The 

following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. 

Request To Update Shop Manual 

Atlas Air requested that the FAA 

revise GE CF6–80C2, ESM 72–53–05, 

High Pressure Turbine (HPT) Rotor 

Thermal Shield—Inspection to add the 

proposed requirement to remove from 

service the HPT thermal shield, the HPT 

rotor stage 1 disk, and the HPT rotor 

stage 2 disk from service if a crack is 

found, since the thermal shield can be 

sent to different vendors outside the 

engine shop. Delta also suggested that 

the technical data within the Engine 

Shop Manual (ESM) should be updated 

to ensure inspection requirements are 

equivalent across all tasks within the 

ESM. 

The FAA disagrees. Requiring updates 

to the ESM is unnecessary to correct the 

unsafe condition identified in this AD. 

The visual and FPI inspections in the 

required actions of this AD are the 

necessary actions to correct the unsafe 

condition. Operators, at their discretion, 

may work with the original equipment 

manufacturer to suggest changes to the 

ESM to include the inspections required 

by this AD. 


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Federal Register / Vol. 86, No. 139 / Friday, July 23, 2021 / Rules and Regulations 38913 

Request To Revise References to Engine 

Manual 

Boeing requested that the FAA update 

reference to the service information in 

the Related Service Information section 

of the NPRM by referencing Revision 90 

of the GE CF6–80A Engine Manual and 

Revision 91 of the CF6–80C2 Engine 

Manual. These revisions of the 

respective engines manuals include 

updated procedures regarding HPT rotor 

Stage 1 and Stage 2 disk serviceability 

for these model engines with respect to 

HPT thermal shield inspection findings. 

The FAA agrees and has updated the 

Related Service Information section of 

this AD as suggested by the commenter. 

Request To Clarify Inspection 

Instructions 

Delta requested that the FAA clarify 

that the mandated visual and FPI 

inspections should be accomplished in 

accordance with the engine manual for 

the affected engine models. 

The FAA disagrees. Operators may 

use any approved method to perform 

the visual and FPI inspections required 

by this AD. 

Request To Clarify Engine Applicability 

United requested that the FAA 

remove CF6–80C2B8F model turbofan 

engines from the applicability of this 

AD. United commented that two HPT 

thermal shield configurations exist, part 

number (P/N) 2787M85P01 and P/N 

9315M41P20. Neither of these 

configurations are applicable to the 

R88DT HPT rotor installed on CF6– 

80C2B8F model turbofan engines. 

United requested that if the FAA 

considers the CF6–80C2B8F turbofan 

engine model affected by this AD, then 

the applicable engine manual should be 

updated to reflect the inspections 

required by this AD. 

The FAA agrees. This AD is not 

applicable to the R88DT HPT rotor 

installed on CF6–80C2B8F model 

turbofan engines because that rotor 

configuration does not have an affected 

thermal shield. The FAA added the 

applicable part numbers for HPT 

thermal shields installed on CF6–80A 

and CF6–80C2 model turbofan engines 

to the applicability paragraph of this 

AD. 

Support for the NPRM 

ALPA supported the NPRM without 

change. 

Conclusion 

The FAA reviewed the relevant data, 

considered any comments received, and 

determined that air safety requires 

adopting this AD as proposed. 

Accordingly, the FAA is issuing this AD 

to address the unsafe condition on these 

products. Except for minor editorial 

changes and any other changes 

described previously, this AD is 

adopted as proposed in the NPRM. 

None of the changes will increase the 

economic burden on any operator. 

Related Service Information 

The FAA reviewed ESM 72–53–00 

High Pressure Turbine Rotor 

Assembly—Disassembly (CF6–80A ESM 

72–53–00), dated February 15, 2020 

from the GE CF6–80A Engine Manual 

GEK72501—Rev 90, dated February 15, 

2021. CF6–80A ESM 72–53–00 

describes procedures for the removal of 

the HPT thermal shield, the HPT rotor 

stage 1 disk, and the HPT rotor stage 2 

disk installed on CF6–80A model 

turbofan engines. 

The FAA also reviewed ESM 72–53– 

00 High Pressure Turbine Rotor 

Assembly—Disassembly (CF6–80C2 

ESM 72–53–00), dated December 1, 

2019 from the GE CF6–80C2 Engine 

Manual GEK92451—Rev 91, dated 

December 1, 2020. CF6–80C2 ESM 72– 

53–00 describes procedures for the 

removal of the HPT thermal shield, the 

HPT rotor stage 1 disk, and the HPT 

rotor stage 2 disk installed on CF6–80C2 

model turbofan engines. 

Costs of Compliance 

The FAA estimates that this AD 

affects 1,084 engines installed on 

airplanes of U.S. registry. 

The FAA estimates the following 

costs to comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Perform FPI and visual inspection of HPT 

thermal shield.

2 work-hours × $85 per hour = $170 ............. $0 $170 $184,280 

The FAA estimates the following 

costs to do any necessary replacements 

that would be required based on the 

results of the inspection. The agency has 

no way of determining the number of 

aircraft that might need these 

replacements. 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replace HPT thermal shield ........................................ 2 work-hours × $85 per hour = $170 ........................... $209,600 $209,770 

Replace HPT rotor stage 1 disk ................................... 2 work-hours × $85 per hour = $170 ........................... 799,700 799,870 

Replace HPT rotor stage 2 disk ................................... 2 work-hours × $85 per hour = $170 ........................... 364,600 364,770 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII: 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

The FAA is issuing this rulemaking 

under the authority described in 

Subtitle VII, Part A, Subpart III, Section 

44701: General requirements. Under 

that section, Congress charges the FAA 

with promoting safe flight of civil 

aircraft in air commerce by prescribing 

regulations for practices, methods, and 

procedures the Administrator finds 

necessary for safety in air commerce. 

This regulation is within the scope of 

that authority because it addresses an 

unsafe condition that is likely to exist or 

develop on products identified in this 

rulemaking action. 


khammond on DSKJM1Z7X2PROD with RULES
38914 Federal Register / Vol. 86, No. 139 / Friday, July 23, 2021 / Rules and Regulations 

Regulatory Findings 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 

substantial direct effect on the States, on 

the relationship between the national 

government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Will not affect intrastate aviation 

in Alaska, and 

(3) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive: 

2021–14–11 General Electric Company: 

Amendment 39–21638; Docket No. 

FAA–2020–1179; Project Identifier AD– 

2020–00818–E. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective August 27, 2021. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to General Electric 

Company (GE) CF6–80A, CF6–80A1, CF6– 

80A2, CF6–80A3, CF6–80C2A1, CF6– 

80C2A2, CF6–80C2A3, CF6–80C2A5, CF6– 

80C2A5F, CF6–80C2A8, CF6–80C2B1, CF6– 

80C2B1F, CF6–80C2B1F1, CF6–80C2B1F2, 

CF6–80C2B2, CF6–80C2B2F, CF6–80C2B3F, 

CF6–80C2B4, CF6–80C2B4F, CF6–80C2B5F, 

CF6–80C2B6, CF6–80C2B6F, CF6– 

80C2B6FA, CF6–80C2B7F, CF6–80C2B8F, 

CF6–80C2D1F, CF6–80C2K1F, and CF6– 

80C2L1F model turbofan engines with an 

installed thermal shield having one of the 

following part numbers: 2787M85P01, 

9315M41P09, 9315M41P13, 9315M41P14, 

9315M41P15, 9315M41P16, 9315M41P20, 

9348M13P01, 9367M63P01, 9367M63P02, 

9367M63P03, 9367M63P04, 9367M63P05, 

9367M63P06, 9367M63P07, or 9315M41P20. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7250, Turbine Section. 

(e) Unsafe Condition 

This AD was prompted by an inspection by 

the manufacturer that revealed cracking of 

the high-pressure turbine (HPT) rotor stage 1 

disk, caused by initial flange-to-flange 

cracking on the HPT thermal shield between 

the HPT rotor stage 1 disk and the HPT rotor 

stage 2 disk. The FAA is issuing this AD to 

prevent failure of the HPT rotor stage 1 disk 

and the HPT rotor stage 2 disk. The unsafe 

condition, if not addressed, could result in 

uncontained release of the HPT rotor stage 1 

and stage 2 disks, damage to the engine, and 

damage to the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) After the effective date of this AD, at 

every piece-part exposure of the HPT rotor 

stage 1 disk, HPT rotor stage 2 disk, or the 

HPT thermal shield, perform a visual 

inspection and a fluorescent penetrant 

inspection of the HPT thermal shield. 

(2) During any inspection required by 

paragraph (g)(1) of this AD, if a crack 

extending through either the forward or aft 

flange of the HPT thermal shield is detected, 

remove the HPT thermal shield, the HPT 

rotor stage 1 disk, and the HPT rotor stage 2 

disk from service. 

(h) Installation Prohibition 

Do not install onto any engine an HPT 

rotor stage 1 disk or HPT rotor stage 2 disk 

that was removed from service due to the 

requirements of paragraph (g)(2) of this AD. 

(i) Definition 

For the purpose of this AD, ‘‘piece-part 

exposure’’ is when the HPT rotor stage 1 

disk, HPT rotor stage 2 disk, or HPT thermal 

shield is separated from their mating rotor 

parts within the HPT rotor module. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, ECO Branch, FAA, has 

the authority to approve AMOCs for this AD, 

if requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ECO Branch, send it to 

the attention of the person identified in 

Related Information. You may email your 

request to: ANE-AD-AMOC@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(k) Related Information 

For more information about this AD, 

contact Kevin M. Clark, Aviation Safety 

Engineer, ECO Branch, FAA, 1200 District 

Avenue, Burlington, MA 01803; phone: (781) 

238–7088; fax: (781) 238–7199; email: 

Kevin.M.Clark@faa.gov. 

(l) Material Incorporated by Reference 

None. 

Issued on June 25, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–15694 Filed 7–22–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0375; Project 

Identifier MCAI–2020–01245–R; Amendment 

39–21656 AD 2021–15–09] 

RIN 2120–AA64 

Airworthiness Directives; Leonardo 

S.p.a. Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Leonardo S.p.a. Model AB139 and 

AW139 helicopters. This AD was 

prompted by two events of 

uncommanded emergency flotation 

system (EFS) deployment during flight. 

This AD requires replacing certain partnumbered EFS control panels and 

prohibits installing them. The FAA is 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective August 27, 

2021. 

ADDRESSES: For service information 

identified in this final rule, contact 

Leonardo S.p.A. Helicopters, Emanuele 

Bufano, Head of Airworthiness, Viale 

G.Agusta 520, 21017 C.Costa di 

Samarate (Va) Italy; telephone +39– 

0331–225074; fax +39–0331–229046; or 

at https://www.leonardocompany.com/ 

en/home. You may view the referenced 

service information at the FAA, Office 

of the Regional Counsel, Southwest 

Region, 10101 Hillwood Pkwy., Room 

6N–321, Fort Worth, TX 76177. For 

information on the availability of this 

material at the FAA, call (817) 222– 

5110. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 


khammond on DSKJM1Z7X2PROD with RULES